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RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAE 104 AIRFOIL (rae104-il)
Reynolds number: 1,000,000
Max Cl/Cd: 58.13 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae104-il-1000000.txt
Download as CSV file: xf-rae104-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 104 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7922   0.06179   0.05998  -0.0378   1.0000   0.0070
 -11.750  -0.8221   0.05450   0.05254  -0.0421   1.0000   0.0067
 -11.500  -0.8529   0.04824   0.04606  -0.0432   1.0000   0.0068
 -11.250  -0.8859   0.04314   0.04074  -0.0416   1.0000   0.0065
 -11.000  -0.9094   0.03936   0.03671  -0.0380   1.0000   0.0066
 -10.750  -0.9379   0.03562   0.03270  -0.0319   1.0000   0.0065
 -10.500  -0.9511   0.03250   0.02928  -0.0271   1.0000   0.0067
 -10.250  -0.9548   0.02977   0.02624  -0.0232   1.0000   0.0068
 -10.000  -0.9513   0.02765   0.02387  -0.0200   1.0000   0.0069
  -9.750  -0.9409   0.02633   0.02236  -0.0176   1.0000   0.0071
  -9.500  -0.9276   0.02535   0.02123  -0.0155   1.0000   0.0072
  -9.250  -0.9232   0.02270   0.01825  -0.0121   1.0000   0.0074
  -9.000  -0.9169   0.02010   0.01535  -0.0088   1.0000   0.0076
  -8.750  -0.9053   0.01854   0.01361  -0.0062   1.0000   0.0078
  -8.500  -0.8911   0.01757   0.01255  -0.0039   1.0000   0.0081
  -8.250  -0.8764   0.01683   0.01174  -0.0017   1.0000   0.0083
  -8.000  -0.8624   0.01616   0.01101   0.0007   1.0000   0.0086
  -7.750  -0.8325   0.01539   0.01015  -0.0003   0.9985   0.0090
  -7.500  -0.8001   0.01475   0.00945  -0.0017   0.9962   0.0096
  -7.250  -0.7681   0.01415   0.00878  -0.0031   0.9936   0.0103
  -7.000  -0.7368   0.01370   0.00828  -0.0041   0.9901   0.0107
  -6.750  -0.7087   0.01238   0.00681  -0.0048   0.9860   0.0115
  -6.500  -0.6767   0.01164   0.00602  -0.0061   0.9833   0.0128
  -6.250  -0.6470   0.01122   0.00557  -0.0069   0.9775   0.0139
  -6.000  -0.6133   0.01083   0.00515  -0.0084   0.9734   0.0152
  -5.750  -0.5797   0.01031   0.00457  -0.0100   0.9689   0.0168
  -5.500  -0.5491   0.00982   0.00407  -0.0109   0.9601   0.0201
  -5.250  -0.5167   0.00955   0.00376  -0.0121   0.9514   0.0225
  -5.000  -0.4882   0.00913   0.00330  -0.0124   0.9396   0.0283
  -4.750  -0.4613   0.00890   0.00303  -0.0123   0.9268   0.0341
  -4.500  -0.4369   0.00861   0.00276  -0.0117   0.9138   0.0473
  -4.250  -0.4131   0.00833   0.00252  -0.0110   0.9016   0.0677
  -4.000  -0.3900   0.00800   0.00230  -0.0102   0.8905   0.1023
  -3.750  -0.3681   0.00758   0.00208  -0.0092   0.8806   0.1599
  -3.500  -0.3468   0.00712   0.00186  -0.0081   0.8714   0.2336
  -3.250  -0.3269   0.00654   0.00163  -0.0069   0.8627   0.3347
  -3.000  -0.3083   0.00590   0.00141  -0.0053   0.8550   0.4553
  -2.750  -0.2905   0.00527   0.00123  -0.0035   0.8472   0.5794
  -2.500  -0.2681   0.00505   0.00120  -0.0023   0.8411   0.6547
  -2.250  -0.2423   0.00497   0.00117  -0.0019   0.8352   0.6832
  -2.000  -0.2159   0.00495   0.00114  -0.0016   0.8297   0.7018
  -1.750  -0.1892   0.00493   0.00113  -0.0013   0.8244   0.7167
  -1.500  -0.1624   0.00491   0.00111  -0.0011   0.8190   0.7299
  -1.250  -0.1354   0.00493   0.00109  -0.0009   0.8139   0.7411
  -1.000  -0.1084   0.00490   0.00110  -0.0007   0.8084   0.7511
  -0.750  -0.0813   0.00490   0.00108  -0.0005   0.8025   0.7598
  -0.500  -0.0542   0.00492   0.00108  -0.0004   0.7966   0.7684
  -0.250  -0.0271   0.00490   0.00108  -0.0002   0.7898   0.7758
   0.000   0.0000   0.00493   0.00108   0.0000   0.7832   0.7831
   0.250   0.0271   0.00490   0.00108   0.0002   0.7757   0.7898
   0.500   0.0542   0.00492   0.00108   0.0004   0.7684   0.7965
   0.750   0.0813   0.00490   0.00109   0.0005   0.7599   0.8025
   1.000   0.1084   0.00490   0.00110   0.0007   0.7509   0.8084
   1.250   0.1354   0.00493   0.00109   0.0009   0.7411   0.8139
   1.500   0.1624   0.00491   0.00111   0.0011   0.7300   0.8190
   1.750   0.1892   0.00493   0.00113   0.0013   0.7167   0.8244
   2.000   0.2159   0.00495   0.00114   0.0016   0.7017   0.8297
   2.250   0.2423   0.00497   0.00117   0.0019   0.6834   0.8352
   2.500   0.2681   0.00505   0.00120   0.0023   0.6542   0.8411
   2.750   0.2906   0.00527   0.00123   0.0035   0.5804   0.8472
   3.000   0.3083   0.00590   0.00141   0.0053   0.4550   0.8550
   3.250   0.3268   0.00655   0.00163   0.0069   0.3336   0.8627
   3.500   0.3468   0.00712   0.00186   0.0081   0.2339   0.8714
   3.750   0.3681   0.00758   0.00208   0.0092   0.1601   0.8806
   4.000   0.3901   0.00800   0.00230   0.0102   0.1028   0.8905
   4.250   0.4131   0.00833   0.00252   0.0110   0.0676   0.9016
   4.500   0.4368   0.00862   0.00276   0.0117   0.0469   0.9138
   4.750   0.4614   0.00889   0.00302   0.0123   0.0345   0.9269
   5.000   0.4882   0.00913   0.00330   0.0124   0.0285   0.9397
   5.250   0.5166   0.00957   0.00377   0.0121   0.0226   0.9515
   5.500   0.5491   0.00981   0.00404   0.0109   0.0202   0.9602
   5.750   0.5799   0.01027   0.00452   0.0099   0.0168   0.9687
   6.000   0.6133   0.01081   0.00513   0.0084   0.0152   0.9733
   6.250   0.6469   0.01122   0.00558   0.0069   0.0140   0.9775
   6.500   0.6766   0.01164   0.00602   0.0062   0.0128   0.9834
   6.750   0.7086   0.01237   0.00681   0.0048   0.0115   0.9860
   7.000   0.7368   0.01367   0.00825   0.0041   0.0107   0.9901
   7.250   0.7679   0.01417   0.00881   0.0031   0.0102   0.9936
   7.500   0.8000   0.01476   0.00946   0.0018   0.0096   0.9961
   7.750   0.8324   0.01540   0.01016   0.0003   0.0089   0.9984
   8.000   0.8623   0.01619   0.01105  -0.0007   0.0086   1.0000
   8.250   0.8764   0.01685   0.01176   0.0017   0.0083   1.0000
   8.500   0.8912   0.01759   0.01257   0.0039   0.0081   1.0000
   8.750   0.9051   0.01861   0.01370   0.0063   0.0079   1.0000
   9.000   0.9165   0.02019   0.01545   0.0089   0.0076   1.0000
   9.250   0.9253   0.02233   0.01783   0.0118   0.0075   1.0000
   9.500   0.9220   0.02631   0.02228   0.0162   0.0073   1.0000
   9.750   0.9348   0.02727   0.02339   0.0183   0.0072   1.0000
  10.000   0.9489   0.02799   0.02424   0.0203   0.0070   1.0000
  10.250   0.9456   0.03092   0.02749   0.0242   0.0070   1.0000
  10.500   0.9491   0.03272   0.02952   0.0273   0.0068   1.0000
  10.750   0.9367   0.03572   0.03280   0.0321   0.0066   1.0000
  11.000   0.9133   0.03894   0.03627   0.0376   0.0067   1.0000
  11.250   0.8892   0.04276   0.04033   0.0414   0.0066   1.0000
  11.500   0.8534   0.04842   0.04627   0.0432   0.0066   1.0000
  11.750   0.8247   0.05431   0.05236   0.0421   0.0066   1.0000
  12.000   0.7928   0.06212   0.06034   0.0376   0.0068   1.0000
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